(2) Maximum permissible manifold pressure;

(3) Maximum permissible gas temperature for turbine engines;

(4) The time limit for use of the power which corresponds with the values established in subparagraphs (1) through (3) of this paragraph;

(5) When the time limit established in subparagraph (4) of this paragraph exceeds 2 minutes, the maximum allowable cylinder head and oil temperatures; and

(6) Maximum cylinder head and oil temperatures if these differ from the maximum limits for continuous operation.

(b) Maximum continuous operation. (1) Maximum rotational speed (r. p. m.); (2) Maximum permissible manifold pressure; and

(3) Maximum

permissible cylinder head, oil, and gas temperatures.

(c) Fuel grade or specification designation. (1) The minimum grade of fuel required for satisfactory operation at the limits specified in paragraphs (a) and (b) of this section for reciprocating engines, and

(2) The designation of the fuel required for satisfactory operation at the limits specified in paragraphs (a) and (b) of this section for turbine engines. [Amdt. 4b-8, 23 F. R. 2591, Apr. 19, 1958] § 4b.718-1 Powerplant limitations governing minimum quantity of antidetonant fluid required for takeoff. (FAA policies which apply to § 4b.718).

The Airplane Flight Manual should include a limitation indicating that the minimum quantity of anti-detonant fluid required is that determined from § 4b.420-1 (a) or (b). If the performance characteristics of the airplane are such that wet power is required for takeoff but may or may not be required for landing, depending upon airport location or characteristics, the Airplane Flight Manual may include information covering minimum allowable quantities under both conditions.

[Supp. 25, 20 F. R. 2281, Apr. 8, 1955]

be those prescribed in §§ 4b.101, 4b.102 and 4b.103. Where the airplane is certificated for more than one center of gravity range, the appropriate limitations with regard to weight and loading procedures shall be set forth in the Airplane Flight Manual for each separate center of gravity range.

[15 F. R. 3543, June 8, 1950, as amended by Amdt. 4b-8, 18 F. R. 2217, Apr. 18, 1953; 18 F. R. 2397, Apr. 24, 1953]

§ 4b.720 Minimum flight crew.

The minimum flight crew shall be established by the Administrator as that number of persons which he finds necessary for safety in the operations authorized under § 4b.721. This finding shall be based upon the work load imposed upon individual crew members with due consideration given to the accessibility and the ease of operation of all necessary controls by the appropriate crew members.

§ 4b.721 Types of operation.

The types of operation to which the airplane is limited shall be established by the category in which it has been found eligible for certification and by the equipment installed. (See the operating rules in this subchapter.)

§ 4b.722 Maximum operating altitude.

A maximum altitude shall be established up to which operation is permitted, as limited by flight, structural, powerplant, functional, or equipment characteristics.

§ 4b.723 Maneuvering flight load fac

(a) Markings and placards shall be displayed in conspicuous places and shall be such that they cannot be easily erased, disfigured, or obscured.

(b) Additional information, placards, and instrument markings having a direct and important bearing on safe operation of the airplane shall be required when unusual design, operating, or handling characteristics so warrant.

a

The air-speed limitations (see § 4b.741 (a)) shall be presented in such manner that they can be easily read and interpreted by the flight crew. [Amdt. 4b-8, 23 F. R. 2591, Apr. 19, 1958] § 4b.733 Magnetic direction indicator.

A placard shall be installed on or in close proximity to the magnetic direction indicator which shall comply with the following.

(a) The placard shall contain the calibration of the instrument in a level flight attitude with engine (s) operating.

(b) The placard shall state whether the calibration was made with radio receiver(s) on or off.

(c) The calibration readings shall be in terms of magnetic headings in not greater than 45° increments.

All required powerplant instruments shall be marked as follows:

(a) The maximum and the minimum (if applicable) safe operational limits shall be marked with red radial lines.

(b) The normal operating ranges shall be marked with a green arc not extending beyond the maximum and minimum safe operational limits.

(c) The take-off and precautionary ranges shall be marked with a yellow arc.

(d) Engine or propeller speed ranges which are restricted because of excessive vibration stresses shall be marked with red arcs.

[Amdt. 4b-6, 17 F. R. 1099, Feb. 5, 1952]

§ 4b.735 Oil quantity indicators.

Oil quantity indicators shall be marked in sufficient increments to indicate readily and accurately the quantity of oil.

§ 4b.736 Fuel quantity indicator.

When the unusable fuel supply for any tank exceeds 1 gallon or 5 percent of the tank capacity, whichever is the greater, a red arc shall be marked on the indicator extending from the calibrated zero reading to the lowest reading obtainable in the level flight attitude. A notation in the Airplane Flight Manual shall be made to indicate that the fuel remaining in the tank when the quantity indicator reaches zero is not usable in flight. (See § 4b.613 (b).)

§ 4b.737

Control markings; general.

All cockpit controls, with the exception of the primary flight controls and other controls the function of which is obvious, shall be plainly marked and/or identified as to their function and method of operation. The markings shall include the following.

(a) Aerodynamic controls. The secondary aerodynamic controls shall be marked to comply with §§ 4b.322 and 4b.323.

(b) Powerplant fuel controls. (1) Controls for fuel tank selector valves shall be marked to indicate the position corresponding with each tank and with all possible cross-feed positions.

(2) When more than one fuel tank is provided, and if safe operation depends upon the use of tanks in a specific sequence, the fuel tank selector controls shall be marked adjacent to or on the control itself to indicate the order in which the tanks should be used.

(3) Controls for engine selector valves shall be marked to indicate the position corresponding with each engine.

(c) Accessory and auxiliary controls. (1) When a retractable landing gear is used, the visual indicator required in § 4b.334 (e) shall be marked so that the pilot can ascertain at all times when the wheels are locked in either extreme position.

(2) Emergency controls, including fuel jettisoning and fluid shutoff controls, shall be colored red and shall be marked to indicate their function and method of operation.

[15 F. R. 3543, June 8, 1950, as amended by Amdt. 4b-6, 17 F. R. 1100, Feb. 5, 1952]

(d) Safety equipment. (1) Safety equipment controls which the crew is expected to operate in time of emergency, such as flares, automatic life raft releases, etc., shall be readily accessible and plainly marked as to their method of operation.

(2) When fire extinguishers and signaling and other lifesaving equipment are carried in lockers, compartments, etc., these locations shall be marked accordingly.

(e) Air-speed placard. A placard shall be installed in clear view of each pilot giving the maximum air speeds for flap extension to the takeoff, approach, and landing positions.

[15 F. R. 3543, June 8, 1950, as amended by Amdt. 4b-6, 17 F. R. 1100, Feb. 5, 1952; Amdt. 4b-3, 21 F.R. 994, Feb. 11, 1956; Amdt. 4b-11, 24 F.R. 7071, Sept. 1, 1959]

AIRPLANE FLIGHT MANUAL

(c) Additional items of information having a direct and important bearing on safe operation shall be required when unusual design, operating, or handling characteristics so warrant.

[15 F. R. 3543, June 8, 1950, as amended by Amdt. 4b-2, 20 F. R. 5309, July 26, 1955] § 4b.740-1 Preparation of airplane flight manuals for aircraft certificated in the transport category (FAA policies which apply to § 4b.740). The primary purpose of the manual is to provide for the crew who will operate the airplane any information concerning the airplane considered by the Federal Aviation Agency essential to or likely to promote safety during such operation. This will ordinarily require a certain amount of descriptive material concerning those parts of the airplane directly operated or otherwise used by the crew, an understanding by them of the nature, location, and functioning of which is therefore essential. The manual should also contain, in order to serve this purpose, a description and chronological outline of the procedure to be followed by the crew during various phases of the operation both "normal" and "emergency" in which special attention and emphasis should be given to any precaution which should be observed therein in the interest of safety.

Another important purpose of the manual is to implement the operating requirements of Parts 40, 41, and 42 of this subchapter; i. e., to furnish a source for all the airplane information necessary to establish the limitations specified by those requirements as well as that necessary to enable the crew readily to operate the airplane within the limitations so established. This purpose requires the inclusion in the manual of all operating limitations peculiar to the airplane under any circumstances likely to be encountered during its life as well as information concerning each of the items of performance involved by Parts 40, 41, and 42 of this subchapter as functions of weight, altitude, outside air temperature, wind velocity, flap setting, etc., throughout the range of these variables for which it is desired by the applicant to provide; the point being that the scheduled operation of the airplane by an air carrier will be limited to values of all such variables within the range(s) covered by information available in the manual. This situation requires that the applicant consider the

extent to which he wishes to limit the usefulness of the airplane subsequent to its certification as a type.

It may be noted, concerning the material to be included in the manual, that two types are involved. The first of these is the operating limitations which are, in effect, a partial statement of the terms upon which the airworthiness certificate is issued. Compliance with these operating limitations is therefore required by law (see section 610 (a) of the Civil Aeronautics Act of 1938 and § 4b.738 (d). The second type of material is the performance information, recommended operating procedures, and loading instructions, the observance or use of which is not legally required of the operator of the airplane by this part, but may be required by Parts 40, 41, and 42 of this subchapter. This second type of material is intended to convey information believed likely to promote or contribute to safety in operation.

The following outlines an acceptable arrangement of the Airplane Flight Manual. This policy does not affect the status of manuals which already have final approval. However, whenever such manuals are revised for other reasons, it is recommended that the terminology of this policy be incorporated wherever it will increase clarity and uniformity. It should be noted that not all the items outlined below for inclusion in the document for a given airplane, and the Federal Aviation Agency is desirous of holding the document to the smallest practicable amount of material as it is believed that the usefulness of the manual will bear some inverse relation to its physical bulk and to the extent of its complexity. It is, therefore, strongly recommended that great care be taken to prepare it in the simplest, most compact form consistent with the completeness and clarity of presentation of the necessary information. Also it is suggested that consideration be given to the likelihood of revisions and the manner in and ease with which this may be accomplished. Only the material (listed below) required by this part should be included in the Federal Aviation Agency approved portion of the manual. However, if desired, the manufacturer or operator may add other data in a distinctly separate section in the same cover. The portion of the material (outlined below) that is to be approved by the Federal Aviation Agency must be so marked, and clearly

separated from any other material so that no one could easily err in regard to the part that is approved. The aircraft specification for the type will list the manual as an item of required equipment and the manual must be made available upon request to any FAA agent issuing an original airworthiness certificate under the type certificate in order that he may verify that the manual furnished with that individual airplane conforms with the approval manual. Since the manual is necessary for safe operation of the airplane, the manual is considered to be public information.

There is no objection to air carrier operators incorporating the subject manual in their own Operations Manual which is assigned to individual crew members in lieu of carrying two separate manuals provided the manual which is furnished by the air carrier includes a separate and properly identified chapter which contains the manufacturer's issue of the FAA Approved Airplane Flight Manual or a satisfactory reproduction identical in both form and contents. The Airplane Flight Manual or its equivalent may, in lieu of individual identification by serial or N numbers, contain a list of the airplane to which the manual is applicable. Such manuals may be installed in the aircraft or be issued to members of the flight crew. Regardless of the procedure in effect, it is the air carrier operator's responsibility to establish a satisfactory system whereby an up-to-date copy of the appropriate manual for the particular airplane is readily available to the flight crew during the operation of the airplane. Inasmuch as the subject manual constitutes a required item of equipment, it is the responsibility of the assigned Air Carrier Maintenance Agent to ascertain that an appropriate and up-to-date copy, or its equivalent, is available to the crew at all times during flight.

The page size for the Airplane Flight Manual will be left to the decision of the manufacturer, although it is believed that an 8" x 101⁄2" size will probably be found most convenient and this size is recommended. A cover should be provided and it should indicate the nature of the contents with the following title: "Airplane Flight Manual." Each page of the approved portion should bear the notation "FAA Approved" and the date of issuance. The material should be bound in a semi-permanent fashion so

that the pages will not be lost easily, yet should be so bound that revised pages can be inserted. The aircraft specification will identify the manual, and when different types of the airplane are covered in separate manuals, each will be listed. Also, the latest approved revisions will be shown on the aircraft specification when these changes are considered to be of major importance to airworthiness.

The Airplane Flight Manual should contain as much of the following as is applicable to the individual model. It is suggested that the document be divided into sections as indicated in paragraphs (a)-(g) of this section. The sequence of sections and of items within sections should follow this outline insofar as practicable. This will facilitate revising the document when an airplane is altered in the field. It is recommended that revisions to the manual resulting from major alterations to the airplane be in the form of supplements to the original manual with individual log of revision pages.

(a) Introduction (1) Title page. This page should include the manufacturer's name, airplane model, registration or serial number, date of approval and space for the signature of the Chief, Aircraft Division. In addition the following note should be included: "This airplane must be operated in compliance with the Operating Limitations herein." (2) Table of contents.

(3) Log of revisions. This page should be in the form of a table in which to record for each revision an identifying symbol, a date, and the page numbers involved. All revised pages should show a revision date and a vertical bar should be placed along the left hand margin to indicate the latest revised portion of each page.

(b) Operating limitations. The purpose of this section is merely to state the limitations without any unnecessary explanation of what they are. The manual should point out that observance of these limitations is required by law.

(1) Weight limits. Indicate the range of maximum take-off and landing weight approved by means of a table or suitable diagram showing these weights at various altitudes throughout the range for which performance information is contained in the manual. State that airplane weight in excess of maximum landing weight must be disposable fuel. limitations on weight.

State any other In addition to

the maximum weights and any relative information, a statement to the effect that the airplane must be loaded in accordance with the approved loading schedule should be included. (See paragraph (e) of this section.) The following is a typical example:

(i) Maximum take-off weight at sea level is 92,000 pounds.

(ii) Maximum landing weight at sea level is 73,000 pounds.

NOTE: This airplane is to be operated in accordance with the approved loading schedule. (See paragraph (e) of this section.) For maximum permissible weights at various altitudes, see paragraph (d), Performance information, of this section. In scheduled or irregular passenger operations, operating weights are limited in accordance with Parts 41, 42, or 61 of this subchapter.

(iii) All weight in excess of the maximum permissible landing weight must consist of disposable fuel.

(iv) All weight in excess of 68,000 pounds must consist of fuel for structural reasons.

(v) All fuel weight must be distributed equally on both sides of the airplane. All main tanks must be filled (equally) first, alternate second, and then auxiliaries. Fuel must be used in reverse order from fuel loading except for take-off, climb and landing-at which time the main tanks should be used.

(2) Center of gravity limits. State all authorized C. G. limits and refer to paragraph (e) of this section for weight and balance data. All C. G. limits should be given in inches from the datum, which should be identified and in percent of the mean aerodynamic chord, with the landing gear extended in all

cases.

(3) Power plant. State all power plant limitations; i. e., manifold pressure, r. p. m., maximum time for use of take-off power, cylinder head and barrel and oil temperatures, minimum fuel octane number, etc. Give any limitation on r. p. m. due to vibration, tip speed, etc.; also propeller pitch, cowl flap position limitations, etc. The items should be listed as follows:

(i) Engine.

(a) Manufacturer. (b) Model.

(c) Propeller drive gear ratio. (d) Fuel, minimum octane.